一种前向追踪拦截方式的滑模制导律研究  

Research on a Head Pursuit Interception Guidance Law based on Sliding Mode Control

作　　者：徐琳[1] 李永强[2] 贾杰[2] 贾晓宏[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]南昌航空大学,江西南昌330063

出　　处：《南昌航空大学学报（自然科学版）》2013年第1期27-30,共4页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：国家自然科学基金(61263012;61263040);中国博士后基金(2012M510593);航空科学基金(20120156001)

摘　　要：在拦截高超音速目标时,传统尾追方式制导律要求拦截弹比目标的速度更快、机动更灵活。针对这一问题,设计了一种前向追踪拦截制导律。首先,建立和分析了前向追踪拦截方式下的弹目运动模型,该方式要求拦截弹在目标前方飞行,且速度比目标速度小;其次,根据滑模控制原理,以目标速度矢量与视线之间的夹角为滑模面,控制拦截弹始终在目标的速度方向上飞行,从而得到该方式下的滑模制导律。经分析发现,该制导律速度要求小,对目标机动不敏感;最后,仿真表明,该制导律所需过载小、拦截精度高。In intercept hypersonic target, the traditional chase mode guidance law requires missile to be faster and more flexible than the target. To solve this problem, this paper designs a head pursuit interception guidance law. First of all,the missile and target motion model in the head pursuit methods is established and analyzed. The head pursuit methods require the missile to fly in front of the target, and the missile speed is smaller than the target speed. Then, according to the sliding mode control theory, the angle between the target velocity vector and the line of sight is set as the sliding surface, and the missile is controlled to always fly in the direction of the target speed. So the sliding mode guidance law is obtained. The analysis finds that the guidance law requires a small speed and is in- sensitive to the target maneuver. The simulation results show that the guidance law requires low overload and has high precision.

关 键 词：前向追踪 拦截 制导律 滑模控制 高超音速 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]